An aircraft blade boot setting tool

Abstract

The present application relates to a kind of aircraft blade bushing setting tool, belong to aerospace technology field, comprising: fixed plate, profiling frame, first setting plate and second setting plate, one end of profiling frame is fixed on fixed plate and its other end is provided with aperture;Fixed plate is provided with with profiling frame inside intercommunication's positioning hole;First setting plate and second setting plate are oppositely spaced and fixed in the two sides opposite to aperture, and define bushing setting area between first setting plate and second setting plate.The present application first one end of profiling frame is fixed on fixed plate, then first setting plate and second setting plate are spaced and fixed in the two sides opposite to aperture of the other end of profiling frame, since define bushing setting area between first setting plate and second setting plate, can avoid metal propeller root sleeve deformation in the production process of composite material blade, improve the qualified rate of blade production.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a kind of aircraft blade bushing setting device. BACKGROUND

[0002] In the production process of composite material blade, metal blade root sleeve deformation occurs, that is, bearing site oval problem, so that the position size is not easy to guarantee when welding eccentric pin seat in later process, eccentric pin seat needs to be reconfigured, and bearing ball and deformation bearing site interact when blade works, so that propeller shell raceway is unevenly stressed, which affects the fatigue life of aluminum alloy propeller shell and propeller performance.

[0003] Therefore, how to design a kind of aircraft blade bushing setting device is a problem to be solved by those skilled in the art. SUMMARY

[0004] The present application provides a kind of aircraft blade bushing setting device, solve the technical problem that metal blade root sleeve deformation easily occurs in the production process of composite material blade.

[0005] The technical scheme for solving the above technical problems is as follows: a kind of aircraft blade bushing setting device, comprising: fixed plate, profiling frame, first setting plate and second setting plate,

[0006] One end of the profiling frame is fixed on the fixed plate, and the other end is provided with an opening;The fixed plate is provided with a positioning hole communicated with the interior of the profiling frame;The first setting plate and the second setting plate are fixed on the opposite sides of the opening, and a bushing setting area is defined between the first setting plate and the second setting plate.

[0007] The beneficial effects of the present application are: first, one end of the profiling frame is fixed on the fixed plate, and then the first setting plate and the second setting plate are fixed on the opposite sides of the opening at the other end of the profiling frame, and since a bushing setting area is defined between the first setting plate and the second setting plate, metal blade root sleeve deformation can be avoided during the production process of composite material blade, and the pass rate of composite material blade production is improved.

[0008] On the basis of the above technical scheme, the present application can also be improved as follows.

[0009] Further, the profiling frame is a trapezoidal frame, the small area end of the trapezoidal frame is fixed on the fixed plate, and the opening is provided at the large area end of the trapezoidal frame.

[0010] Further, the opposite side surfaces of the first setting plate and the second setting plate are flat, and the opposite side surfaces of the second setting plate and the first setting plate are curved.

[0011] A further beneficial effect of the above-mentioned method is that the side surfaces of the first shaping plate and the second shaping plate close to each other are designed to be a plane and a curved surface respectively. Since the propeller sleeve shaping area is located between the plane and the curved surface, it can better fit on the outer peripheral side of the metal propeller sleeve of the composite blade, thereby improving the shaping effect of the metal propeller sleeve.

[0012] Furthermore, it also includes a plurality of reinforcing plates, which are arranged at intervals on the outer periphery of the profiling frame and whose adjacent sides are respectively fixed on the fixing plate and the profiling frame.

[0013] A further beneficial effect of the above method is that the structural strength of the shaping tooling can be improved by using multiple reinforcing plates fixed to the fixed plate and the profiling frame respectively.

[0014] Furthermore, the plurality of reinforcing plates are all of right-angled trapezoidal structure and two adjacent right-angled sides thereof are respectively fixed on the fixing plate and the contoured frame.

[0015] Furthermore, it also includes a plurality of support blocks, which are respectively located between the second shaping plate and the opposite sides of the opening and fixed at intervals on the opposite sides of the opening; the second shaping plate is fixed on the plurality of support blocks.

[0016] The above-mentioned further beneficial effect is that the second forming plate is supported by multiple supporting blocks, which can improve the stability of the second forming plate, avoid deformation of the propeller sleeve forming area, and improve the shaping effect of the metal propeller root jacket.

[0017] Furthermore, it also includes a positioning ring, which is fixed on the plate surface of the fixing plate away from the contour frame, and the ring hole of the positioning ring is arranged opposite to the positioning hole.

[0018] Furthermore, it also includes multiple fixing bolts. The profiling frame is provided with multiple fixing holes at intervals on the frame body corresponding to the surrounding side of the opening. The first shaping plate and the second shaping plate are both provided with threaded holes corresponding to the multiple fixing holes; the multiple fixing bolts respectively pass through the fixing holes and are screwed into the corresponding threaded holes. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the left side three-dimensional structure of an aircraft blade cover shaping tool of the present invention;

[0020] Figure 2 This is a schematic diagram of the right side three-dimensional structure of an aircraft blade cover shaping tool of the present invention;

[0021] Figure 3 This is a front structural schematic diagram of an aircraft blade cover shaping tooling according to the present invention;

[0022] Figure 4It is a rear view structure schematic diagram of the aircraft blade sleeve setting tool.

[0023] In the drawings, the components represented by each reference numeral are listed as follows:

[0024] 1, fixed plate, 11, positioning hole, 2, profiling frame, 3, first setting plate, 4, second setting plate, 5, reinforcing plate, 6, supporting block, 7, positioning ring, 8, fixing bolt. DETAILED DESCRIPTION

[0025] The principles and characteristics of the present application are described below in conjunction with the drawings, and the examples are only used to explain the present application and are not used to limit the scope of the present application.

[0026] As shown in Figure 1 An aircraft blade sleeve setting tool, comprising: a fixed plate 1, a profiling frame 2, a first setting plate 3 and a second setting plate 4,

[0027] One end of the profiling frame 2 is fixed on the fixed plate 1 and the other end is provided with an opening; the fixed plate 1 is provided with a positioning hole 11 communicating with the inside of the profiling frame 2; the first setting plate 3 and the second setting plate 4 are fixed on the opposite sides of the opening and define a sleeve setting area between the first setting plate 3 and the second setting plate 4.

[0028] In some embodiments, the profiling frame 2 is a trapezoidal frame, the small area end of the trapezoidal frame is fixed on the fixed plate 1, and the opening is provided at the large area end of the trapezoidal frame.

[0029] In some embodiments, the opposite side of the first setting plate 3 and the second setting plate 4 is a plane, and the opposite side of the second setting plate 4 and the first setting plate 3 is a curved surface.

[0030] In some embodiments, a plurality of reinforcing plates 5 can be further included, the plurality of reinforcing plates 5 are arranged at the outer circumferential side of the profiling frame 2 and the adjacent two sides are respectively fixed on the fixed plate 1 and the profiling frame 2.

[0031] In some embodiments, the plurality of reinforcing plates 5 can all be right-angled trapezoidal structures and the adjacent two right-angled sides are respectively fixed on the fixed plate 1 and the profiling frame 2.

[0032] In some embodiments, a plurality of supporting blocks 6 can be further included, the plurality of supporting blocks 6 are respectively located between the second setting plate 4 and the opposite opening side and are fixed on the opposite opening side; the second setting plate 4 is fixed on the plurality of supporting blocks 6.

[0033] In some embodiments, a positioning ring 7 can be further included, the positioning ring 7 is fixed on the plate surface of the fixed plate 1 away from the profiling frame 2 and the ring hole is arranged opposite to the positioning hole 11.

[0034] In some specific embodiments, a plurality of fixing bolts 8 can also be included, the profiling rack 2 is provided with a plurality of fixing holes at intervals on the rack body corresponding to the hole circumferential side, the first shaping plate 3 and the second shaping plate 4 are both provided with threaded holes corresponding to the plurality of fixing holes; the plurality of fixing bolts 8 respectively pass through the fixing holes and are screwed into the corresponding threaded holes.

[0035] The above is only the preferred embodiment of the present application, and is not used to limit the present application, any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An aircraft propeller blade sleeve shaping tool, characterized in that: include: Fixed plate (1), A profiling frame (2), one end of the profiling frame (2) is fixed on the fixing plate (1) and the other end thereof is provided with an opening; the fixing plate (1) is provided with a positioning hole (11) communicating with the interior of the profiling frame (2); A first shaping plate (3) and a second shaping plate (4), wherein the first shaping plate (3) and the second shaping plate (4) are fixed at opposite sides of the opening at a relative interval and define a paddle sleeve shaping area between the first shaping plate (3) and the second shaping plate (4); The profiling frame (2) is a ladder frame, the small-area end of the ladder frame is fixed on the fixing plate (1), and the opening is provided at the large-area end of the ladder frame; It also includes a plurality of reinforcing plates (5), which are arranged at intervals on the outer periphery of the profiling frame (2) and whose adjacent sides are respectively fixed to the fixing plate (1) and the profiling frame (2); It also includes a plurality of support blocks (6), wherein the plurality of support blocks (6) are respectively located between the second shaping plate (4) and the opposite sides of the opening and are fixed on the opposite sides of the opening at intervals; the second shaping plate (4) is fixed on the plurality of support blocks (6); It also includes a plurality of fixing bolts (8), the profiling frame (2) is provided with a plurality of fixing holes at intervals on the frame body corresponding to the peripheral side of the opening, and the first shaping plate (3) and the second shaping plate (4) are both provided with threaded holes corresponding to the plurality of fixing holes; the plurality of fixing bolts (8) respectively pass through the fixing holes and are screwed into the corresponding threaded holes.

2. The aircraft propeller blade sleeve shaping tool according to claim 1, characterized in that: The side surfaces of the first shaping plate (3) and the second shaping plate (4) opposite to each other are plane surfaces, and the side surfaces of the second shaping plate (4) and the first shaping plate (3) opposite to each other are curved surfaces.

3. The aircraft propeller blade cover shaping tool according to claim 1, characterized in that: The plurality of reinforcing plates (5) are all of right-angled trapezoidal structure, and two adjacent right-angled sides thereof are respectively fixed on the fixing plate (1) and the contoured frame (2).

4. The aircraft propeller blade cover shaping tool according to claim 1, characterized in that: It also includes a positioning ring (7), which is fixed on the plate surface of the fixing plate (1) away from the contour frame (2), and the ring hole of the positioning ring is arranged opposite to the positioning hole (11).

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